EP0708227B1 - Faserverstärkte Turbomaschinenschaufel mit integrierter Bürstendichtung und deren Herstellungsweise - Google Patents

Faserverstärkte Turbomaschinenschaufel mit integrierter Bürstendichtung und deren Herstellungsweise Download PDF

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Publication number
EP0708227B1
EP0708227B1 EP95402066A EP95402066A EP0708227B1 EP 0708227 B1 EP0708227 B1 EP 0708227B1 EP 95402066 A EP95402066 A EP 95402066A EP 95402066 A EP95402066 A EP 95402066A EP 0708227 B1 EP0708227 B1 EP 0708227B1
Authority
EP
European Patent Office
Prior art keywords
blade
brush
resin
fibers
seal
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP95402066A
Other languages
English (en)
French (fr)
Other versions
EP0708227A1 (de
Inventor
Monique André Thore
Pascal Claude Michel Adrien Vasseur
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0708227A1 publication Critical patent/EP0708227A1/de
Application granted granted Critical
Publication of EP0708227B1 publication Critical patent/EP0708227B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
    • F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
    • F16J15/3288—Filamentary structures, e.g. brush seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/56—Brush seals
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the subject of the invention is a dawn of composite material turbomachine comprising a seal brush at its free end as well as its method of production.
  • the invention finds application in the aeronautics.
  • FIG 1 there is shown schematically an airplane engine turbomachine conventionally comprising a low compressor pressure referenced 1, a high pressure compressor referenced 3, and a blower, referenced 5.
  • the high pressure compressor 3 has a fixed part, namely the stator 3a whose blades 3b are maintained by their fixed ends on the casing 2; he further comprises a rotary part, namely the rotor 3c whose 3d blades are fixed by their ends fixed to rotating discs 3c.
  • the compressor low pressure 1 has a fixed stator and a rotor 1b rotary.
  • the blower 5 has a blade 6 rotary and a fixed part, the casing 7.
  • One of these seals is made in an abradable material, that is to say a material to honeycomb structures, of the honeycomb type, which is positioned on the fixed elements of the turbomachine (on casings or stators) in line with the elements turning (rotor or blade).
  • abradable material that is to say a material to honeycomb structures, of the honeycomb type, which is positioned on the fixed elements of the turbomachine (on casings or stators) in line with the elements turning (rotor or blade).
  • FIG 2 there is shown, according to a longitudinal section, a seal of this type applied to a blower.
  • This figure 2 shows therefore, schematically, a portion of blower 5 comprising a casing 7 and a rotary vane 6.
  • a seal 8 located at the right of dawn 6.
  • This seal 8 is produced made of an abradable material of the honeycomb type.
  • brush seals such as seals is also known to limit gas leaks in turbomachinery.
  • the document FR-A-379 209 describes different stages of turbines with movable blades at the end free of each of which is added a ring fitted with a brush seal.
  • a brush seal is simply reported on the free end of dawn.
  • the brush seal can tear off from this blade. The brush seal then loose in the turbomachine can, of course, cause untoward damage.
  • the object of the present invention is precisely remedy the disadvantages of seals proposed above.
  • the invention relates a turbomachine blade made of composite material produced using a fabric of multidirectional fibers impregnated with a resin and comprising a blade body having a fixed end and a free end.
  • a turbomachine blade made of composite material produced using a fabric of multidirectional fibers impregnated with a resin and comprising a blade body having a fixed end and a free end.
  • This dawn of a turbomachine is characterized by the fact that it has a seal at the free end of the blade body waterproofing integrated in the resin.
  • the seal includes a plurality of specific fibers which are partly integrated in the resin and partly outside the blade body to form a brush.
  • the specific fibers are integrated into the resin at an angle opposite to the direction of rotation of the turbomachine.
  • the specific fibers are metallic.
  • this process can include a machining operation to adjust the length of the fibers.
  • the blades according to the invention are produced made of composite material, i.e. they are made with woven and impregnated fibers of a resin.
  • Many documents describe processes for producing blades of composite material, for example, patent FR-A-2,684,719, patent FR-A-2 682,992, or even US-A-4,354,804.
  • the blades made of material composite can therefore be used in areas relatively cold turbomachinery, such as compressors.
  • FIGS. 3A, 3B and 3C we have very schematically shown, a sectional view longitudinal of the free end of three blades each comprising a brush seal produced according to a different embodiment of the invention.
  • FIG 3A there is shown the free end of the blade 6 of the fan 5 shown in Figure 1.
  • This blade 6 made in composite material therefore consists of a fabric of fibers 10 impregnated with a resin 12. These fibers 10 are called, in the description, basic fibers of composite material.
  • FIG. 3A there is shown, in in addition, additional fibers 11, also called specific fibers or added fibers.
  • These fibers specific 11 are integrated into the material composite realizing dawn 6. As we can see on the figure, these specific fibers 11 are partly introduced into the resin 12 of the composite material. In in addition, a portion of these specific fibers 11 is outside dawn 6, i.e. it exceeds dawn. The portion of these fibers 11 which is out of the blade constitutes a brush 9 (or brush seal).
  • FIG 3B there is shown a second embodiment of the brush seal 9 of the blade 6.
  • the brush 9 is produced, on the one hand, by means of the specific fibers 11 and, on the other hand, by means of reinforcing fibers 13.
  • These reinforcing fibers 13 are fibers constituting the composite material, of a length higher than that of the base fibers 10 shown in Figure 3A. These reinforcing fibers 13 therefore protrude outside dawn 6 just like the specific fibers 11 so as to densify the brush 9 produced by these specific fibers 11.
  • FIG. 3C a third embodiment of the brush seal 9 of a blade 6 of composite material.
  • the brush seal 9 is made, a fold on two, by means of specific fibers 11 and fibers of base 10 and every other fold using fibers reinforcement 13.
  • each specific fiber 11 is aligned with a basic fiber 10.
  • Dawn 6 is therefore made with a fiber fabric including both base 10 fibers and reinforcement 13.
  • Such an embodiment allows to obtain a denser brush seal 9 than that shown in Figure 3A.
  • the fiber fabric impregnated can be machined at an angle to give the brush a certain tilt.
  • FIG 4 there is shown, according to a front view of the turbomachine, one free end a blade 6 having a brush seal 9 inclined by angle ⁇ with respect to the axis X of the blade 6. This angle ⁇ is opposite to the direction of rotation of the vane 6. From this so, when the blade 6 is rotating, the brush 9 comes to rub on the track of the casing 7, which ensures a good seal, since the brush 9 is in permanently in contact with runway 7.
  • FIG. 5 there is shown, according to a longitudinal section view of the turbomachine, the free end of the blade 6 with, in part, the fabric of fibers making the brush seal 9.
  • This FIG. 5 therefore shows the embodiment in which the fabric of fibers has superimposed pleats or a multidirectional weaving. More specifically, we can see in this figure 5 that the fibers realizing, both the composite material of blade 6 and the seal brush 9 can be woven so multidirectional, which achieves a brush seal 9 better sealing and a more solid blade 6.
  • the housing 7 and, in general, all elements against which brush seals rub according to the invention, are metallic or even composite material with a metal track to the place where the brush seals 9 rub, the tracks of friction to the right of the brush seals to have a good polished surface, so as to allow the best possible seal.
  • the fibers reported are metallic fibers.
  • the housing 7 or all element against which a brush seal is in contact has a track that has received a very smooth deposit of chromium carbide.
  • these brush seals according to the invention can be made for all kinds of fixed or mobile elements, if these elements are made of composite materials.
  • the use of integrated brush seals according to the invention makes it possible to replace the abradable material of fixed elements by a simple friction track, which allows to lighten substantially the casing of the turbomachine.
  • the housing can be lightened by 10.7 kg.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Sealing Devices (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (7)

  1. Turbomaschinenschaufel aus einem Verbundwerkstoff, die mittels eines harzgetränkten Gewebes aus in mehreren Richtungen verlaufenden Fasern (10, 13) hergestellt ist und einen Schaufelkörper (6) aufweist,
       dadurch gekennzeichnet,
       daß sie an dem freien Ende des Schaufelkörpers eine in das Harz integrierte Dichtung (9) aufweist.
  2. Turbomaschinenschaufel nach Anspruch 1, dadurch gekennzeichnet, daß die Dichtung eine Anzahl spezifischer Fasern (11) umfaßt, die zum Teil in das Harz integriert sind und zum Teil außerhalb des Schaufelkörpers liegen, um eine Bürste zu bilden.
  3. Turbomaschinenschaufel nach Anspruch 2, dadurch gekennzeichnet, daß die spezifischen Fasern unter einem der Drehrichtung der Turbomaschine entgegengesetzten Winkel a in das Harz integriert sind.
  4. Turbomaschinenschaufel nach Anspruch 2 oder 3, dadurch gekennzeichnet, daß im Bereich des freien Endes des Schaufelkörpers ein Teil des Fasergewebes nicht mit Harz bedeckt ist, so daß es mit den spezifischen Fasern eine dichtere Bürste bilden.
  5. Turbomaschinenschaufel nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, daß die spezifischen Fasern aus Metall bestehen.
  6. Verfahren zur Herstellung einer Turbomaschinenschaufel (6) aus einem Verbundwerkstoff, die eine Dichtung (9) aufweist,
       gekennzeichnet durch die Verfahrensschritte:
    Einbringen eines Fasergewebes (10, 13) in eine Form,
    Einbringen von spezifischen Fasern (11) in die Form im Bereich des freien Endes des Schaufelkörpers,
    Einspritzen eines Harzes (12) in die Form,
    Durchführen einer Polymerisation des harzgetränkten Fasergewebes unter einer Heiz-presse,
    Auflösen des Harzes durch einen chemischen Angriff in einem Säurebad an dem freien Ende der Schaufel in Höhe der spezifischen Fasern (11), um eine gewünschte Bürstenlänge zu erhalten.
  7. Verfahren nach Anspruch 6, gekennzeichnet durch den weiteren Verfahrensschritt, daß die Länge der Fasern durch materialabtragende Bearbeitung eingestellt wird.
EP95402066A 1994-09-14 1995-09-13 Faserverstärkte Turbomaschinenschaufel mit integrierter Bürstendichtung und deren Herstellungsweise Expired - Lifetime EP0708227B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9410949A FR2724412B1 (fr) 1994-09-14 1994-09-14 Aube de turbomachine en materiau composite munie d'un joint d'etancheite et son procede de realisation
FR9410949 1994-09-14

Publications (2)

Publication Number Publication Date
EP0708227A1 EP0708227A1 (de) 1996-04-24
EP0708227B1 true EP0708227B1 (de) 1998-11-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP95402066A Expired - Lifetime EP0708227B1 (de) 1994-09-14 1995-09-13 Faserverstärkte Turbomaschinenschaufel mit integrierter Bürstendichtung und deren Herstellungsweise

Country Status (4)

Country Link
US (1) US5628622A (de)
EP (1) EP0708227B1 (de)
DE (1) DE69506074T2 (de)
FR (1) FR2724412B1 (de)

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US9938848B2 (en) * 2015-04-23 2018-04-10 Pratt & Whitney Canada Corp. Rotor assembly with wear member
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US10724540B2 (en) 2016-12-06 2020-07-28 Pratt & Whitney Canada Corp. Stator for a gas turbine engine fan
US10690146B2 (en) 2017-01-05 2020-06-23 Pratt & Whitney Canada Corp. Turbofan nacelle assembly with flow disruptor

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Also Published As

Publication number Publication date
US5628622A (en) 1997-05-13
FR2724412B1 (fr) 1996-10-25
DE69506074D1 (de) 1998-12-24
DE69506074T2 (de) 1999-04-22
EP0708227A1 (de) 1996-04-24
FR2724412A1 (fr) 1996-03-15

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